介绍了一种“前缘空腔”高超声速被动流动控制方法并将其应用于轴对称钝锥外形,采用高分辨率的CFD数值模拟方法对不同参数的前缘空腔外形进行了对比研究,阐述了高超声速前缘空腔降低前缘壁面热流的机理,总结了不同空腔参数对空腔外形气动力、热的影响规律。结果表明,合理设计空腔参数可以使空腔外形的前缘壁面热流有较大程度的降低,并且不影响外形的升阻比等气动特性。 A “leading-edge cavity” hypersonic passive flow control method is introduced and applied to an axisymmetric blunt cone shape. The shape of the leading-edge cavity with different parameters is compared by a high-resolution CFD numerical simulation The mechanism of the hypersonic leading edge cavity in reducing the heat flow of the leading edge wall was discussed. The influence of different cavity parameters on the aerodynamic and thermal characteristics of the cavity was summarized. The results show that the reasonable design of the cavity parameters can make the heat flow in the front wall of the cavity profile to a great extent and does not affect the aerodynamic characteristics such as the aspect ratio and the drag ratio.